Various standard airfoils are used in aviation, wind turbine blade designs, and for other applications that rely on aerodynamic forces. The rapid evolution of computing methods now allows you to accurately calculate the flow behavior of the airfoil in the short term. In this study, the aerodynamic performance of the NACA 63-215 and NACA 65-421 standard airfoils created by the National Aeronautics Advisory Committee (NACA) was analyzed with two-dimensional computational fluid dynamics. These analyses were performed on a 1 × 10⁶ Reynolds number and at different attack angles to discover better aerodynamic performance. Spalart-Allmaras, the standard k-ε and standard k-ω turbulence models are evaluated comparatively based on experimental data. Finally, the results and comparison of various properties i.e., drag and lift coefficients, pressure distribution over the airfoils are presented to help the user choose the right airfoil, and the turbulence model for a wing design or other aerodynamic modelling corresponds.